Aeroplane



D. AMICI.

AEBOPLANE.

IIIIIIIIIIIIIIIII AN. 8, 1920.

Patented Apr. 5, 1921.

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244. AtHUNAU l lUb D. AMICI.

AEROFLANE.

APPLICATION FILED JAN. 3, I920.

V Patented Apr. 5, 1921.

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D. AMlCi.

AEROPI AN'E. APPLICATION FILED IAN- 3, 1920.

Patented Apr. '5, 1921.

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D. AMICI.

.. AERUPLANE APPLICATION FILED JAN- 8. [9201 I P 3 1,373,934. I Patented Apr. 0, 1921.

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INVENTOR.

Z44. AIZHUNAU l IUD UNITED STATES PATENT OFFICE.

AEROPLAN'E.

Specification of Letters Patent.

Patented Apr. 5, 1921.

Application filed January 8, 1920. Serial No. 350,069.

To all whom it may concern:

Be it known that I, DOMENICO AMioi, a subject of the King of Italy, residing at WVoodland, in the county of Yolo and State of California, have invented new and useful Improvements in Aeroplanes, of which the following is a specification.

The present invention is directed to improvements in aeroplanes, and has for its primary object to provide a device of this character having wings capable of being quickly folded or unfolded.

A further object of the invention is to provide novel means for quickly foldingor unfolding the wings whether the machine is in motion or at a standstill.

Another object of the invention is to provide an aeroplane so constructed that the wings may be folded rearwardly to reduce the wing area to permit the machine to pass between restricted spaces, as for instance, between buildings, trees, or other objects, and to permit a number of machines to be stored in a hangar.

Still another object of the invention is to provide novel means for locking the wings in folded or unfolded positions, said means being operable through the medium of a motor independent of the propelling motor.

An embodiment of the invention is illustrated in the accompanying drawings, wherein Figure l is a perspective view of the device showing the wings unfolded.

Fig. 2 is a top plan view, the wings being unfolded.

Fig. 3 is a top plan view, the wings being folded.

Fig. 4 is a side elevation of the device, the fuselage being shown in outline and the wings removed to more clearly illustrate the wing manipulating mechanism.

Fig. 5 is a front elevation of the wing manipulating mechanism.

Fig. 6 is a detail perspective view ofthe wing manipulating and locking mechanism.

Fig. 7 is a plan view of the ratchet disk.

Fig. 8 is a detail view showing the relative position of the locking pawls and ratchet teeth.

Fig. 9 is a detail perspective view of the hinge for connecting the wings to the fuse la e.

Fig. 10 is a side elevation of the landing device.

Fig. 11 is a sectional view on line 11-11 of Fig. 10.

Fig. 12 is a sectional view on line 12-12 of Fig. 10.

Fig. 13 is a sectional view on line 13-13 of Fig. 2.

Fig. 14 is a detail front elevation of one of the strut connecting brackets.

Referring to the drawings, 1 designates the fuselage, which may be of any well known form, and associated therewith is the propeller 2, which is driven in the conventional manner.

Fixed to the fuselage 1 are brackets 3, to the forward ends of which are bolted plates 4;. Pivotally connected between the plates 4 are the forward ends of springs 5, said springs having bolted intermediate their ends boxes 6, which support the axle 7. This axle carries the running wheels 8 in the usual manner. Inverted U-shaped clips 9 straddle the brackets 3, the rear ends of the springs 5 being pivotally connected to said clips. The bight portions of these clips are formed with perforations 10, and engaged therein are bolts 11, the lower ends of which are engaged with the brackets 3. Surrounding the upper portions of the bolts 11 are coil springs 12, the lower ends of which rest on the clips 9, while their upper ends engage the heads of the bolts 11. These clips 9 are permitted to move vertically with respect to the brackets 3, the upward movement of said clips being cushioned by the springs 12. When the machine is landing or running over the ground the shock imparted to the wheels 8 is initially absorbed by the springs 5, and finally absorbed by the springs 12. A rear running wheel 13 is suitably connected to the rear end of the fuselage 1.

The wings 14 consist of upper and lower frames 15 and 16, respectively, and comprise front bars 17 and rear spaced tracks 18, said tracks being fixed to brackets 19. The brackets 19 are pivotally connected to the rear ends of the transverse bars 20, the forward ends of which are similarly connected to the front bars 17. The frames 15 and 16 are held in proper spaced vertical position by struts 21 and 22, the latter having their ends connected to the brackets 19, as clearly shown in Fig. 14.

Associated with the fuselage 1 are vertical bars 23, the lower ends of which are coupled to the rod 24 arranged transversely of the fuselage, while their upper ends are coupled to a bar 24 disposed above the fuselage, and has carried thereby a bearing 25, the purpose of which will appear later.

Associated with the bars 23 and 24 are ferrules 25, and hingedly connected thereto, as at 26, are ferrules 27 which have fixed therein the inner ends of the bars 17, as clearly shown in Figs. 5 and 9.

Fixed to the inner ends of the bars 17 and tracks 18 are angle arms 28 and 29, the latter being pivotally connected by rods 30, similar rods 31 being also employed for connecting the former. Having their forward ends pivotally connected with the arms 28 are convergingly arranged links 32, said links having their rear ends plvotally connected with the rear end of the bar 33. The forward end of the bar 33 is formed with a rack 34 which meshes with a pinion 35. The pinion 35 is fixed to the upper end of the shaft 36, which has its upper end journaled in the bearing 25, and its lower end rotatably associated with the bar 24.

Slidably keyed to the shaft 36 is a collar 37 which may be shifted vertically through the medium of the hand lever 38, said lever being in convenient reach of the pilots seat 39. Formed integral with the upper end of the collar 37 is a friction disk 40, while a similar disk 41 is carried by the lower end .of said collar.

An electric motor 42 is supported within the fuselage 1, and its shaft 43 is provided with a friction disk 44, said disk being located between the disks 40 and 41, and normally out of contact therewith, but may be readily placed in engagement with either one upon shifting the lever 38. Thus it will be seen that the collar 37 may be shifted to place the disk 40 or 41 in engagement with the disk 44, thereby imparting rotary movement to the shaft 36. In this manner the bar 33 is shifted through the medium of the pinion and rack 34 in the direction clesired to fold or unfold the wings 14.

It is obvious that when the disk 44 is in frictional contact with the disk 41 the shaft 36 will be rotated anti-clockwise, and through the medium of the pinion 35 and rack 34, the bar 33 will be slid forwardly, thus folding the wings 14. Of course when the disk 44 is engaged with the disk 40 the movement of the rod 33 will be reversed, thus unfolding the wings 14.

It is necessary to lock the shaft 36 against rotation in both directions to hold the wings in their folded or unfolded positions, and to accomplish this a ratchet disk 45 is fixed to the shaft 36 adjacent its lower end. This disk has its upper face formed with circular series of ratchet teeth 46 and 47, said teeth being directed in opposite directions. Spring pressed pawls 48 and 9 engage the respective teeth 46 and 47 and it will be noted that should both pawls be out of engagement with the ratchetteeth that the shaft 36 could rotate in either direction. It is essential, however, that one of the pawls be engaged with the respective teeth when the wings are folded or unfolded to prevent accidental rotation of the shaft 36 in either direction. In Fig. 6 both pawls are shown in engagement with the respective teeth, and consequently the shaft 36 cannot rotate in either direction. However, when the pawl 48 is engaged with the teeth 46 and the pawl 49 is disengaged from the teeth 47 the shaft 36 and disk 45 will be held against anti-clockwise rotation, and when the pawls are in the reverse position said disk and shaft are held against clockwise rotation. Since the ratchet teeth 46 and 47 are arranged in opposite directions it is obvious that when the disk 45 is being rotated, and one of the pawls is raised the other pawl will ride over the associated teeth.

These pawls 48 and 49 are provided, respectively, with treadles 50 and 51, said treadles being pivotally supported within the fuselage in any suitable manner, and in convenient reach of the pilots foot.

The frames 15 and 16 are each provided with planes 52, preferably of canvas, but it will be apparent that any other material suitable for the purpose may be utilized. These planes have their forward edges suitably secured to the front bars 17 while their rear edges are suitably connected with the wheels 53, which are adapted to travel between the tracks 18, and are grooved for engagement therewith, as clearly shown in Fig. 13. Thus it will be seen that the planes 52 will be permitted to fold neatly when the frames 15 and 16 are folding. Since the wheels 53 are associated with the tracks 18 it is obvious that the planes 52 will be tightly stretched when the wings are in their unfolded or operative positions.

A supplemental rigid plane 54 is supported in any suitable manner above the forward end of the fuselage 1, and between the inner ends of the planes 52.

\Vhen it is desired to fold the wings 14 the disk 41 is shifted upwardly into contact with the disk 44, and since this disk is driven from the motor shaft 43 rotary movement is imparted to the shaft 36 and pinion 35. This movement of the shaft rotates the pinion and causes the rack 34 to draw the bar 33 forwardly, whereupon the links 32 push the rods 31 correspondingly. Since the rods 31 are pivotally connected to the angle arms 28 it is obvious that the arms 29 as well as the arms 28 will be swung forwardly thus causing the frames 15 and 16 to swing on the hinge connections 26, thereby compelling the front bars 17 and tracks 18 to swing rearwardly and toward each other until the wings are folded substantially in parallel relation with respect to the fuselage 1, as shown in Fig. 3. It will be of course understood that when the disk 41 is being driven by the disk 44 to fold the wings 14 that the pawl 48 will be raised from engagement with the teeth 46, thereby permitting the disk 45 to rotate. As the disk 45 rotates anti-clockwise the pawl 49 will ride over its associated teeth 47. As soon as the wings are properly folded the pawl 48 is dropped into engagement with the teeth 46, but it is the pawl 49 that prevents a reverse rotation of the disk 45, thereby preventing accidental unfolding of the wings 14.

To unfold the wings it is only necessary to shift the disk 40 into contact with the disk 44 whereupon movement to the bar 33 and angle arms 28 and 29 is reversed and the bars 17 and tracks 18 swing outwardly until the wings are in the desired position. It is obvious that the pawl 49 should be held from engagement with the teeth 47 while the wings are unfolding, and at which time the pawl 48 is riding over the teeth 46. As soon as the wings are in their proper extended or unfolded positions the pawl 49 is dropped into engagement with the teeth 47 Since the teeth 46 and 47 are directed in opposite directions and the pawls engaged with the respective teeth rotary movement of the shaft 36 and its associated parts are positively prevented. The disk 44 is of course shifted to its neutral position after the wings have been folded or unfolded.

From the foregoing description it will be apparent that an aeroplane has been pro vided with wings which may be easily and quickly folded when it is desired to move the same from place to place without rising in the air. Since the wings can be folded the aeroplane can be transported over streets or roads where the space is restricted under the power of its propeller.

Any suitable means for guiding the aeroplane may be used, and any suitable brake may be employed to retard the speed thereof when the device is traveling on the ground.

What is claimed is:

1. In a aeroplane, the combination with the fuselage, of a pair of wings hingedly connected thereto, angle arms associated with the inner ends of the wings, a shaft, friction disks slidably associated with the shaft, means operable by the shaft and connected with the angle arms for folding or unfolding the wings, a disk fixed to the shaft and having oppositely directed teeth thereon, means for alternately engaging the friction disks to rotate the shaft in opposite directions, and means pivotally supported on the fuselage for detachably engaging the teeth to normally hold the shaft against rotation in opposite directions.

2. In an aeroplane, the combination with the fuselage, of a pair of wings hingedly connected therewith, angle arms associated with the inner ends of the wings, a shaft, connections between the arms and shaft, a motor for operating the shaft, and means carried respectively, by the shaft and fuselage for locking the shaft against rotation in opposite directions.

3. In an aeroplane, the combination with the fuselage, of a pair of folding wings hingedly connected therewith, said wings comprising upper and lower frames consisting of front bars, brackets, transverse bars pivotally connecting the front bars and brackets, tracks supported by the brackets, wheels movable on the tracks, flexible planes having their forward edges fixed to the front bars and their rear edges connected with the wheels, and means for folding or unfolding the wings.

4. In an aeroplane, the combination with the fuselage, of wings hingedly connected therewith, a shaft, a pair of disks slidably associated with the shaft, a third disk fixed to the shaft and having oppositely directed ratchet teeth thereon, means for alternately driving the paired disks in opposite directions, means operable by the shaft to fold or unfold the wings, and pawls for engaging the ratchet teeth to normally hold the shaft against rotation in opposite directions.

In testimony whereof I have hereunto set my hand in the presence of two subscribing witnesses.

DOMENICO AMICI.

Witnesses:

G. E. TOOTHAKER, R. G. LAWSON. 

